Abstract: A rotor (20) for a compressor, in particular in a gas turbine, has a number of rotor blades (25) which are arranged around the rotation axis of the rotor (20) in the form of a rim and are each held in a circumferential recess (21) on the rotor (20) by a blade root (26), with the blade root (26) having a widening lower part (27) which engages behind two shoulders (24) that are formed on the side walls of the recess (21). In such a rotor, the life is lengthened in that the recess depth (T) of the recess (21) is substantially greater than a minimum recess depth (Tmin) which results in the rotor (20) having sufficient strength in the area of the blade attachment for starting, based on the predetermined material characteristics of the rotor (20) and the operating conditions of the compressor.

Abstract: A rotor of a thermally loaded turbomachine, in particular of a compressor or a gas turbine, is mounted such that it can rotate about a rotor axis and is concentrically surrounded by a hot-gas duct or cooling-air duct. A significant improvement to the ability of the rotor to withstand thermal loads is achieved, with little increased outlay in terms of materials, by virtue of the fact that the rotor comprises a rotor core made of a first material, that the rotor core is concentrically surrounded by shielding rings made of a second material, which shield the rotor core from the temperature in the hot-gas duct or cooling-air duct, the second material having a higher heat resistance than the first material, and that the shielding rings are cohesively joined to the rotor core.

Abstract: A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.

Abstract: A mechanical mount axially and radially secures a device, such as a fan, to a shaft of a motor without a need for setscrews or keyways. Elimination of a keyway and setscrew for securing a fan to a motor shaft minimizes stress that the fan is subjected to during its operation. Certain exemplary embodiments of a system of the present invention comprising: a device; a mount of hardened material having a insertion edge with a concave shape secured to the device; and a shaft including an axial groove having a concave shape and a circumferential groove, wherein the mount along the insertion edge is insertable within the axial and circumferential groove, the concave shape of the insertion edge of the mount and the shape of the axial groove promoting a secure fit between the shaft and the mount to substantially prevent movement of the device.

Abstract: A rotor disk for a turbomachine, the disk carrying blades whose roots are retained in a peripheral groove of the disk, the groove including a window for inserting blade roots and a locking member that is a single elastically deformable piece and dimensioned to be received and retained in a notch of the groove while in its free state, and to be capable of being displaced to slide inside the groove while in a stressed and elastically deformed state.

Abstract: A retaining key for a turbine nozzle includes a key body having top and bottom surfaces, a pair of sides and a pair of ends including a forward end having a pair of horizontal shoulders on opposite sides of a center rib, the shoulders located substantially midway between the top and bottom surfaces such that the forward end has a substantially inverted T-shaped profile, and a rearward end having a first surface portion extending from and substantially perpendicular to the top surface and a second surface portion extending at an acute angle downwardly and toward the forward end and intersecting the bottom surface.

Abstract: The invention relates to a disk/blade assembly for an aircraft engine compressor, comprising a disk (2) and a plurality of blades with hammer attachment (6), each blade comprising a blade root provided with an upstream bearing surface (32) situated on a leading edge side of the airfoil and a downstream bearing surface (34) situated on a trailing edge side of this airfoil, the disk being provided with a circumferential groove (10) in which the blade root of each of the blades is held by means of the bearing surfaces. According to the invention, for each of the blades, the downstream bearing surface (34) is offset circumferentially from the upstream bearing surface (32) in a given direction of offset (42), corresponding to the direction of offset between the trailing edge (22) and the leading edge (20) of the airfoil.

Abstract: A turbine engine and a rotor for a turbine engine are provided. Several adjacent turbine blades are positioned in the circumferential direction of the rotor, each turbine blade having a blade root, each turbine being fixed in a retainer groove, running in the circumferential direction of the rotor, by means of the blade root. Each turbine blade may be introduced, by the blade roots thereof, into the retaining groove, by means of a filling groove, whereby the width of the filling groove is matched is matched to the width of the blade roots. The width of the blade roots (13, 14) and the width of the, or each filling groove (17) in the circumferential direction is greater than half the width of a desired nominal blade pitch (18), whereby in the region of the, or each filling groove (17), a first number of turbine blades (11) with desired nominal blade pitch (18), is exchanged for a second number of turbine blades (12), with increased blade pitch (19), the first number being greater than the second number.

Abstract: A rotor end piece (1) for a rotor (6) of a thermal turbomachine, having at least one circumferential slot (3) in which moving blades and intermediate pieces are provided, includes a residual gap (15) formed between an end blade (2) and an end part (11), in which residual gap (15) two end piece halves (4, 4) are arranged which have securing tabs (8, 8) which are in each case connected to the latter in one piece and are in engagement with the end blade (2) and with the end part (11), respectively.

Abstract: Rhombic shrouded tangential entry buckets are circumferentially applied to the rotor wheel rim of a turbine. A fixture is releasably secured to a lug on each bucket and includes a chamfered surface for engaging a complementary surface on the lug. Upon applying a tangential assembly force, the shroud and airfoil of adjacent buckets are pre-twisted in a rotational direction about a generally radial axis enabling dovetail faces to contact one another notwithstanding interference fit shroud contacting surfaces. The removal of the fixture from the lug enables the bias of the airfoil to rotate the shroud in an opposite direction into final assembly with the shroud edges of adjacent buckets in contact with one another and the dovetail faces thereof in contact with one another.

Abstract: A rotor end piece (1) for a rotor of a thermal turbomachine, having at least one circumferential slot (3) in which press blades, intermediate pieces and two end blades (4), between which a residual gap is formed, are fitted, the rotor end piece (1) having two end piece halves (9, 9) and a wedge (7), is characterized in that a clip (8) is arranged in the residual gap, this clip (8) absorbing the forces of the two end piece halves (9, 9) and two shim halves (5, 6) arranged between the end piece halves (9, 9) and restrained with the wedge (7). As a result, the disadvantages of the prior art are avoided and a rotor end piece is provided which exerts no axial forces on the rotor and no forces on adjacent blades in the circumferential direction, so that an occurrence of disturbing rotor vibrations and jamming of adjacent blades is effectively avoided.

Abstract: A rotor end piece for a rotor of a thermal turbomachine having a circumferential slot includes two end piece halves having side faces opposite one another in the installed state and top surfaces adjoining one another, the side faces of the end piece halves being connected to one another in a form-fitting manner by means of a dovetail interlocking connection, and a whole intermediate end piece having a top surface, the two interlocked end piece halves being firmly connected to the whole intermediate end piece in the region of the top surfaces via a weld.

Abstract: The steampath for a steam turbine includes stacked stator rings each mounting inwardly directed nozzles and stacked rotor wheels each mounting outwardly directed buckets mounting blades. By alternately stacking the stator rings and rotor wheels, the nozzles and buckets of the various stages are interdigitated to form a steampath. Each bucket includes a blade and a root received in a generally complementary shaped groove on a wheel.

Abstract: A locking arrangement for a row of radial entry blades (62) of a turbo-machine. A closing blade (66) includes a root portion (74) having an axial attachment shape (78) for engagement with an axially oriented slot having an axial attachment shape (76) formed at the entering slot location (34) of the radial entry rotor disk (56). For applications utilizing blades with curved platform faces (112), a preceding blade (108) and a following blade (110) in the row are designed with one curved face for abutting adjacent radial entry blades and one flat face (120) for abutting the flat closing blade faces (116). The closing blade (84) may be designed with a root portion (88) having two legs (90,92) that are urged apart by a key (86) into tight contact with the adjacent blades.

Abstract: A turbomachine rotor wheel comprises a disk carrying blades having roots engaged and held in an annular recess of the disk, the roots being connected to platforms for co-operating with an annular gasket mounted in an annular groove of the disk, the annular sealing gasket exerting a resilient force on the blade platforms holding the blades in a proper position for operation while the turbomachine is at rest.

Abstract: The invention relates to a rotor end piece (1) for rotors (2) of thermal turbomachines with a circumferential slot (3), consisting of two end piece halves (4, 4?) having side faces (5, 5?) opposite one another in the installed state and of a wedge (6) which is pushed in between them and which, in the installed state, is anchored in the side faces (5, 5?) of the end piece halves (4, 4?) in a form-fitting manner, the rotor end piece (1) being arranged in the axial direction of the rotor (2) between two moving blades (7, 7?). It is characterized in that each of the end piece halves (4, 4?) is fastened in the axial direction of the rotor (2) to the two adjacent moving blades (7, 7?) by means of one interlocking connection (8, 8?, 9, 9?) each. These four interlocking connections (8, 8?, 9, 9?), instead of the rotor (2), now absorb the axial forces which are caused by the centrifugal force and the caulked wedge (6). In this way, disturbing rotor vibrations are advantageously avoided.

Abstract: A fixing method for blading of a fluid-flow machine, in which first of all the turbine blades (31, 32) are inserted into the fastening slot (1) of a rotor (2) or stator until only the intermediate fitting gap is left, into which two insert elements designed as end piece halves (41, 42) are then inserted. After that, a wedge (6) is inserted into the gap between the end piece halves (41, 42), and the end piece halves (41, 42) together with the wedge (6) are welded by a joining weld (10). With the method according to the invention and the arrangement according to the invention, axial forces which can warp the rotor (2) and thus cause increased rotor vibrations are advantageously avoided. The invention also relates to a fixing arrangement according to the invention.

Abstract: The invention relates to a bladed disk for a turbomachine, the disk including blades which extend into a conical stream and which are held in a peripheral groove of said disk by hammerhead type fasteners, each of said blades further including a platform whose radially-outer face defines the boundary of the gas flow stream and whose radially-inner face presents an upstream rib and a downstream rib disposed in planes that are perpendicular to the axis of rotation of said disk and that are radially adjacent respectively to an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove in order to provide leaktightness in these zones, wherein the thickness of the downstream rib in the axial direction is greater than the thickness of the upstream ring.

Abstract: A rotor end piece (1) for rotors (2) of thermal turbormachines is provided with circumferential slot (3), including two end piece halves (4, 4?) having side faces (5, 5?) opposite one another in the installed state and top surfaces (6, 6?) adjoining one another. The rotor end piece (1) side faces (5, 5?) of the end piece halves (4,4?) are connected to one another in a form-fitting manner. To this end, the side faces (5, 5?) are designed in such a way that a dovetail interlocking connection of the two end piece halves (4, 4?) is preferably realized. The interlocked end piece halves are then secured with a weld (8). The firm anchoring of the rotor end piece (1) achieved in this way prevents detachment during operation and damage to the turbomachine caused as a result.

Abstract: The invention relates to an axial-flow thermal turbomachine having a metallic rotor (1), in which rotor blades (3) made of an intermetallic compound are mounted in a circumferential groove to form a row of blades. The invention is characterized in that at least two rotor blades (3?) which are at a uniform distance from one another and are made of a more ductile material are arranged in the said row of blades between the intermetallic rotor blades (3), the rotor blades (3?) made of the more ductile material either being considerably longer than the intermetallic blades (3) or, if they are of the same length, having a different blade tip shape than the intermetallic blades (3).

Abstract: The invention relates to an axial-flow thermal turbomachine, having a rotor (1) made from a metallic material with a first density (D1), in which rotor blades (3, 3?) and intermediate pieces (4) are mounted alternately in a circumferential groove. It is characterized in that said intermediate pieces (4) consist of a material with a second density (D2), which is lower than the first density (D1). Particularly suitable materials for the intermediate pieces (4) are intermetallic compounds, preferably intermetallic ?-titanium aluminide alloys or intermetallic orthorhombic titanium aluminide alloys, but also titanium alloys.

Abstract: The invention relates to a method of improving the retention capacity of a blade having an asymmetrical hammerhead connection and extending in a conical stream, with the root of the blade being retained in a peripheral groove in a disk, said groove having an upstream lip and a downstream lip presenting respective bearing surfaces that extend in planes that are asymmetrical relative to planes perpendicular to the axis of rotation of said disk, and against which the surfaces of the upstream and downstream flanks of said root come to bear, the bearing surface of said upstream lip being connected to the bottom wall of said groove via a rounded surface, and the upstream flank presenting, in the vicinity of said rounded surface, a heel situated inside a circle of radius R centered on the axis about which said blade tends to pivot when axial stress is applied thereto, said circle outlining, in the upstream lip, a crescent shape of thickness e, wherein: a) the connection between the bearing surface of the upstream

Abstract: The drum of the invention is generally in the form of a body of revolution about a longitudinal axis, being made of a metal alloy and extending between an upstream end and a downstream end along a curved profile capable of being circumscribed in an annular envelope extending around said longitudinal axis, said profile extending radially about a surface of revolution presenting a generatrix line, said downstream end being provided with a stiffener. In characteristic manner, said stiffener is provided with at least one composite assembly mounted on said downstream end, said composite assembly comprising fibers and a polymer matrix. The drum is preferably for use in constituting a rotor of a low pressure compressor.

Abstract: System for connecting and locking blades which are fixed circumferentially to a rotor disc (1) of an axial compressor, comprising a plurality of blades (10, 10?) positioned in an array along the circumference of rotor disc (1), each blade (10, 10?) being provided with a shaped root (13) for connection to the rotor disc (1), and a dowel for positioning and locking the blades (10, 10?) in a predetermined position in a circumferential seat (3) which has a shaped profile and which is formed along the circumference of the rotor disc (1). At least one insertion slot (4) intersects the circumferential seat (3) to permit the insertion of the roots (13) of the blades (10, 10?) and the dowel.

Abstract: An outer rotor structure for the ac fan mainly comprises a plurality of annular pole plates used to stack each other to form an outer rotor. Each of the pole plate includes an axial hole, a plurality of poles, at least one aligning member and a plurality of recessions. The aligning member is used to align the two adjacent pole plates for stacking so that the recessions of the pole plate are turned a slight angle in stacked relationship with those of the adjacent pole plate. The longitudinally connected recessions are formed a plurality of assembling members adapted to mount ends of metal blades therein at predetermined positions by welding.

Abstract: The invention relates to a device for immobilizing blades in the peripheral slot of a turbomachine disk. Said blades comprise roots of the hammer head type adapted to be introduced into said slot through a loading window and held in said slot by collaboration of shape with the sidewalls thereof. Said immobilizing device is adapted to be introduced into said slot through said loading window and comprises a locking element arranged in a space separating two adjacent blade roots. Said locking element is adapted to be raised up into a lock housing formed in the sidewalls of said slot under the action of a radial manipulating screw the head of which rests against the bottom of the slot, a radial clearance being provided between the bottom of the slot and the underside of the blade roots, and said screw head being restrained in a radially outward direction by said two adjacent blade roots.

Abstract: A turbomachine, in particular a gas turbine, includes a rotor which extends along an axis of rotation. The rotor includes a circumferential face, which is defined by the outer radial boundary surface of the rotor, and a receiving structure. Additionally, it includes a first rotor blade and a second rotor blade, which each have a blade root and a blade platform. The blade platform of the first rotor blade and the blade platform of the second rotor blade adjoin one another, and a space is formed between the blade platforms and the circumferential face. A sealing system is provided on the circumferential face in the space, the sealing system including a labyrinth sealing system.

Abstract: Airfoils and grooves on the rotor or carrier for the airfoils have generally complementary dovetail shapes. The airfoils are installed in the grooves by sliding the bases of the airfoils along the circumferential grooves into final circumferential positions. At each circumferential position, a pin is driven between the base of the airfoil and the bottom of the groove to displace the airfoil radially into a final radially secured position taking up the clearance necessary to enable sliding movement of the airfoils about the groove. A first tool is used to drive each pin in a generally tangential direction by hammering on the end of the tool, transmitting an axial force to the pin. When the circumferential clearance of the last installed airfoil is insufficient to permit further use of a tangentially oriented tool to install additional airfoils, a second tool having an angled head is disposed into the groove to engage the pin.

Abstract: An apparatus is described for detecting the early signs of cycle-induced fatigue and thereby predicting failure of the rotating disk in turbo-machinery. It identifies asymmetrical growth of hub-blade diameter as a predictor of incipient crack growth. Tip measurements are processed through specialized algorithms to detect such asymmetry during operation, providing a real-time, non-destructive method of prediction. The sensors can be housed within the machinery case, and are capable of operating in harsh environments while maintaining adequate stand-off distance, making the entire apparatus robust enough for conditions in high-speed turbo-machinery.

Abstract: A steam turbine wheel has a male dovetail projecting about its peripheral margin and a gap in the margin. Buckets having bases with complementary female dovetails are disposed in the gap and register with the male dovetail of the wheel, enabling the buckets to slide about the wheel into positions stacking the bases of the buckets against one another. The final three buckets including a closure bucket are disposed about the wheel margin with two buckets straddling the closure bucket secured to the wheel margin by the dovetails. The closure bucket is secured to the straddling buckets by axially extending pins. The closure and straddling buckets, as well as the pins, are formed of materials having a higher creep rupture strength than the materials forming the remaining buckets, enhancing the capability of the closure bucket to withstand high temperature and stresses over time without creep.

Abstract: A turbine disc for carrying turbine blades is rotatable about a central axis and has a circumferentially extending peripheral face divided into two side face strips by a circumferentially extending root slot. For the greater part of its circumferential length opposite sides of the root slot are parallel. But at at least one location arcuate bights of opposite curvature are formed opposite to one another to form a load slot through which a root of a turbine blade can be introduced into the radially innermost part of the root slot. The arcuate bights have the same radius of curvature and may be arcs of the same circle. On each of two opposite sides of the load slot is a respective shadow slot. One shadow slot is formed by oppositely disposed arcuate bights, and the other shadow slot is formed by oppositely disposed arcuate bights. The radius of curvature of each bight of the shadow slot is greater than that of the bights of the load slot and can be at least twice that of the bights of the load slot.

Abstract: The invention relates to hammer-fastener blade-locking device affixing the blades in the channel (2) of a turbojet-engine rotor disk (1) and comprising a case (15) of which the cross-section matches that of the channel (2), further a locking element (16) mounted in radially displaceable manner in a traverse orifice in the case (15) and receivable in part in a lock housing (9a, 9b), and a drive bolt (17) acting on the locking element (16). The locking element (16) comprises stops (32a) sliding in windows (22a) of the case (15). The bolthead (4) is large and is radially affixed between the bottom of the channel (2) and the base (20) of the case (15).

Abstract: The blades (3) of a turbine of axial design are inserted into an undercut blade groove (2) of the turbine rotor (1) in a positive-locking manner and are secured by a blade lock. The blade lock comprises a mounting space (7), which is in connection with the blade groove (2) and into which a filler piece (8), which is in positive-locking relationship with the blade foot (6) of the blades (3), and a wedge (9) are inserted. The cross section of the mounting space (7) receiving the filler piece (8) is widened conically beginning from the blade groove (2). The cross section of the filler piece (8) is adapted to the cross section of the mounting space (7).

Abstract: A turbine closure bucket adapted to complete assembly of a row of tangential entry buckets on a rotor wheel includes an airfoil portion and a mounting portion for mounting the bucket to a turbine wheel. The mounting portion has front and back faces, with weight reduction cavities formed internally in the front and back faces. Externally, the front and back faces of the closure bucket are substantially identical to front and back faces of adjacent buckets in the row.

Abstract: A rotor (1) of a turbomachine comprises a basic rotor element (2) and a multiplicity of rotor blades (3, 3′, 3″, 3′″). The rotor blades (3, 3′, 3″, 3′″) are arranged in a distributed manner in at least one row on the circumference of the basic rotor element (2). An area for a row of guide vanes is furthermore provided in front of and/or behind the row of rotor blades. A heat shield element (4) or a plurality of heat shield elements (4′, 4′, 4′″) lined up on the circumference of the rotor (1) is arranged in such a way between the basis rotor element (2) and the rotor blades (3, 3′, 3″, 3′″) of the row of rotor blades that the basic rotor element (2) is completely covered in the areas of the row of rotor blades and the row of guide vanes.

Abstract: The present invention relates to a guide vane stage of a compressor comprising an outer ring and an inner ring, both of which are concentric and preferably circular. The rings are connected to each other via a series of fixed vanes, characterized in that at least one of the rings is provided with a series of holes or apertures which allow the vanes to pass through these holes or apertures. The fixed vanes also have, at at least one of their ends, an aperture to allow at least one locking element to pass through, making it possible to simultaneously securely fasten all the present in the guide vane stage, on the non-functional side of the ring. The end of the fixed vanes through which the locking element passes is buried in an elastomeric element.

Abstract: A turbine disc for carrying turbine blades is rotatable about a central axis and has a circumferentially extending peripheral face divided into two side face strips by a circumferentially extending root slot. For the greater part of its circumferential length opposite sides of the root slot are parallel. But at at least one location arcuate bights of opposite curvature are formed opposite to one another to form a load slot through which a root of a turbine blade can be introduced into the radially innermost part of the root slot. The arcuate bights have the same radius of curvature and may be arcs of the same circle. On each of two opposite sides of the load slot is a respective shadow slot. One shadow slot is formed by oppositely disposed arcuate bights, and the other shadow slot is formed by oppositely disposed arcuate bights. The radius of curvature of each bight of the shadow slot is greater than that of the bights of the load slot and can be at least twice that of the bights of the load slot.

Abstract: The invention relates to hammer-fastener blade-locking device affixing the blades in the channel (2) of a turbojet-engine rotor disk (1) and comprising a case (15) of which the cross-section matches that of the channel (2), further a locking element (16) mounted in radially displaceable manner in a traverse orifice in the case (15) and receivable in part in a lock housing (9a, 9b), and a drive bolt (17) acting on the locking element (16). The locking element (16) comprises stops (32a) sliding in windows (22a) of the case (15). The bolthead (4) is large and is radially affixed between the bottom of the channel (2) and the base (20) of the case (15).

Abstract: Moving blades of a fluid-flow machine are fastened in a circumferential slot on the rotor by means of blade roots. For the installation of the last moving blade, a gap is provided between the first and penultimate blade. After the latter has been fitted, a residual gap remains in the circumferential slot, and this residual gap is filled by means of whole intermediate pieces and halved intermediate pieces (7a, 7b), which are arranged between the moving-blade roots. According to the invention, the inner sides (8) of the halved intermediate pieces (7a, 7b), which inner sides (8) face the center of the circumferential slot, are of hook-shaped design. In this case, the inner side (8) of one half (7a) of a halved intermediate piece forms the geometric negative of the inner side (8) of the other half (7b) of the halved intermediate piece. As a result, the two halves (7a, 7b) can be connected to one another in a positive-locking manner.

Abstract: A balance weight has first and second margins at right angles to one another with the second margin larger than the first margin. A balance weight groove in a rotor has outer and inner wall portions, with the outer wall portions spaced a distance less than the spacing between the inner wall portions. The balance weight has a central threaded opening receiving a screw and a driving slot in the upper face of the weight. An insertion tool is threaded to the balance weight to insert the balance weight through a turbomachinery access opening into the groove. The tool is rotated to locate the second margins below the outer wall portions of the groove. By inserting a driving tool through the insertion tool, the screw is rotated to lock the balance weight to the rotor and in the groove. Upon removal of the insertion and driving tools, a staking tool is inserted through turbine access opening to stake the balance weight and rotor and the screw and balance weight.

Abstract: A final kit of a selected plurality of first and second groups of articles, for example turbine engine blading members, for subsequent assembly within a tolerance range along a distance in an article holder, is provided prior to assembly in the holder. This is accomplished by measuring dimensions of the first and second groups, and adjusting, if necessary, the numbers of articles in each group while maintaining the total number in the plurality.

Abstract: A rotor blade includes an airfoil, an integral platform, and a dovetail integrally joined to the platform. The dovetail includes a neck extending between a pair of dovetail lobes configured to engage a complementary slot in a rotor disk. The dovetail includes an undercut extending between an outer face of the dovetail lobes and the neck for introducing a stress concentration thereat. The stress concentration relieves stress at the outer face at the expense of the neck for increasing the high cycle fatigue life of the blade.

Abstract: In an arrangement for fixing blades (5) to a rotor (1) or stator, a number of slots (7) which run helically on the circumferential surface of the body to be fitted with blades are provided, filling pieces (6) which serve to space apart the blades (5) and fix the blades (5) in a frictional manner being present between individual blade rows (3).

Abstract: An arrangement for the thermal protection of a rotor, fitted with moving blades, of a high-pressure compressor. The roots of the moving blades are inserted and locked in peripheral grooves which are at an axial distance from one another. The rotor has, between two adjacent peripheral grooves for the moving blades, at least one further peripheral groove having a hook extending over the entire periphery of the rotor. At least two plate-shaped heat-accumulation segments, each having at least one root which has a contour adapted to the hook of the rotor so that both form a contact area, are pushed radially one after the other into the further peripheral groove and locked therein. A cavity forming an insulating layer extends between the heat-accumulation segments and the rotor and between the moving-blade roots and the rotor, in which insulating layer the velocity of the compressor air is greatly reduced.

Abstract: A ceramic blade for a hybrid type gas turbine blade has a dovetail portion, a platform portion formed on the dovetail portion and blade portions formed on the platform portion. The number of the blade portions formed on one platform portion is two or more. The upper surface of the platform portion is shaped into an arc-like form, and the dovetail portion is linearly formed in a tangential direction to a turbine rotation direction. By the utilization of this blade, the hybrid type gas turbine blade can inhibit the leakage of a gas and can be easily manufactured and is excellent in durability.

Abstract: An assembly (12) for moving air through a heat exchanger (10) comprising a shroud (14) for mating with a heat exchanger (10) and a fan (20) disposed in the rear opening (18) of the shroud (14). The fan (20) comprises a hub (22) having an axis (A) and blades (24) extending radially from the hub (22) to distal ends for moving air through the shroud (14). The assembly is characterized by a bearing ring mechanism (28, 30) interconnecting the distal ends of the blades (24) and the shroud (14) for rotatably supporting the fan (20) solely by the shroud (14). The bearing ring mechanism (28, 30) includes a ring (28) surrounding and interconnecting the distal ends of the fan blades (24) a guideway (30) in the shroud (14) supporting and retaining a head (32) extending from the ring (28) for rotation relative to the shroud (14).

Abstract: A turbocompressor disk having on its periphery a circular groove able to receive blade roots having a substantially hammer shape, said circular groove comprising an upstream lip and a downstream lip against which bear the blade roots. The upstream lip has a curvature of gradient inclined by an angle .alpha. with respect to the plane perpendicular to the rotation axis and the downstream lip has a curvature of gradient inclined by an angle .beta. with respect to the plane perpendicular to the rotation axis, .alpha. being strictly different from .beta..

Abstract: In a bladed rotor of an axial-flow turbomachine, the blades essentially consist of a blade body and a blade root. They are fastened with their blade roots in rows in encircling blade grooves having lateral supporting prongs. A shoulder serving to assemble the blades on the rotor is attached between blade body and blade root. The blade grooves are shaped symmetrically to the associated planes of symmetry by a plurality of radii (R1-R4), the preceding radius (R1) in each case being larger than the following radius (R2). The circular arcs formed by the radii (R1-R4) have a common tangent (T) at their contact points.

Abstract: A compressor having an axially divided casing, includes a plurality of casing halves. Guide vanes are fastened by their roots in peripheral grooves. Distributed over the periphery, bolts are introduced, which are anchored in the groove base of the peripheral groove. These bolts preferably project radially into the peripheral groove and divide the guide vanes into aggregates and end aggregates situated at the partition plane of the casing.

Abstract: In a drum rotor (1) for an axial-flow turbomachine, the blades are fastened with their roots (3) in rows in encircling blade grooves (10) having lateral supporting prongs. At least the first blade groove (10), on the inlet side of the working medium, is shaped in an axially asymmetrical manner by a plurality of radii (R1-R4). The preceding radius (R1) in each case is larger than the following radius (R2), and the circular arcs (21-24) formed by the radii (R1-R4) have a common tangent (T) at their contact points.